MODEL 560

MODEL 560 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration REVISIONS As new information becomes available for your airplane, revisions will be issued to all registered owners. It is the pilot’s responsibility to assure that this flight manual is complete and current at all times. REVISED MATERIAL INDICATORS Two types of revised material indicators will be used in this manual. A change bar located in the left margin adjacent to the applicable text will extend the full length of new pages and deleted, new, or revised text added on presently existing pages. A change bar in the footer will indicate a revision to the footer and/or that some text has slipped to or from that page. A bar will extend the full length of deleted, new or revised text added on new or presently existing pages. This bar will be located adjacent to the applicable text in the margin on the left side of the page. A bar located adjacent to the figure number in the margin on the left side of the page will be used to indicate that the figure number only has changed. An asterisk located at the end of a figure number will be used to indicate that an illustration has been revised or is all new material (Ex: Figure 3-4* ). All revised pages will carry the revision number opposite the page number on the applicable page. A list of revisions is located at the beginning of the Log of Effective Pages. DEFINITIONS Performance definitions are available in Section IV; the remaining definitions are listed as follows: WARNING OPERATING PROCEDURES, TECHNIQUES, ETC., WHICH WILL RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED. CAUTION OPERATING PROCEDURES, TECHNIQUES, ETC., WHICH WILL RESULT IN DAMAGE TO EQUIPMENT IF NOT CAREFULLY FOLLOWED. NOTE An operating procedure, technique, etc., which is considered essential to emphasize. (Continued Next Page) 56FMC-00 1-4 AA MODEL 560 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration DEFINITIONS (Continued) LAND AS SOON AS POSSIBLE Land at the nearest suitable airport. Extreme situations could require off airport landing. Primary consideration is safety of occupants. LAND AS SOON AS PRACTICAL Land at a suitable airport. The primary consideration is the urgency of the emergency or abnormal situation. Continuing to the destination or an alternate with appropriate service facilities, may be an option. EMERGENCY PROCEDURES An emergency procedure is one requiring the use of special systems and/or regular systems in order to protect the occupants and the airplane from serious or critical harm. These procedures require immediate action. ABNORMAL PROCEDURES An abnormal procedure is one requiring the use of special systems and/or the alternate use of regular systems which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk resulting from a failure condition. NORMAL PROCEDURES A normal procedure is one which may be thought of as routine in day-to-day flying. ADVISORY INFORMATION Section VII of this manual provides guidance information not approved by the FAA. 1-5 56FMC-00 AA MODEL 560 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane, and have been incorporated into this manual. This list contains only those Service Bulletins that are currently active. Number Title Airplane Serial Effectivity Revision Incorporated Incorporated in Airplane 56FMC-00 1-6 AA MODEL 560 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration AIRPLANE CONFIGURATION CODES The following is a list of airplane configuration codes which appear at the bottom of each page of this FAA Approved Airplane Flight Manual. The codes indicate page effectivity by serial number. This list contains only the configurations which have been incorporated into this manual. Configuration Code Effectivity by Serial Number AA Airplanes 560-0751 and On. AA 1-7/1-8 56FMC-00 MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration OPERATING LIMITATIONS TABLE OF CONTENTS Page OPERATING LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Certification Status . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Weight Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Center-of-Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Weight and Balance Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Powerplant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 Battery and Starter Cycle Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Ground Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Hydraulic Fluid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Approved Oils . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Single Point Refueling Limitation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 Fuel Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 Unusable Fuel. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Speed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Takeoff and Landing Operational Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Ice and Rain Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Operations in Severe Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Performance Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Enroute Operational Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Operations Authorized . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Boundary Layer Energizers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Minimum Crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Takeoff/Landing/Enroute Temperature Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Maximum Maneuvering Speeds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 Load Factor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Cabin Pressurization Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Passenger Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Angle-of-Attack/Stick Shaker System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Airplane Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-20 Rockwell Collins FCS-3000 Integrated Flight Control System . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-20 Standby Flight Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-20 Supplemental Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 High Frequency (HF), Automatic Direction Finder (ADF) Systems. . . . . . . . . . . . . . . . . . . . . . . . 2-21 Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 GND IDLE Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 Tail Deice System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 2-1/2-2 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration OPERATING LIMITATIONS NOTICE CERTIFICATION STATUS This airplane is certified in accordance with 14 CFR Part 25. WEIGHT LIMITATIONS Maximum Design Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17,030 Pounds Maximum Design Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16,830 Pounds Maximum Design Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15,200 Pounds Maximum Design Zero Fuel Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12,600 Pounds Takeoff weight is limited by the most restrictive of the following requirements: Maximum Certified Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16,830 Pounds Maximum Takeoff Weight Permitted by Climb Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Procedures for Use of Takeoff Performance Tables in Section IV Takeoff Field Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Procedures for Use of Takeoff Performance Tables in Section IV Landing weight is limited by the most restrictive of the following requirements: Maximum Certified Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15,200 Pounds Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limit . . . . . . . . . Refer to Procedures for Use of Approach and Landing Performance Tables in Section IV Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Procedures for Use of Approach and Landing Performance Tables in Section IV Maximum Nose Baggage Compartment Weight. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 310 Pounds Maximum Tail Baggage Compartment Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 500 Pounds Minumum weight in RVSM airspace . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,800 Pounds CENTER-OF-GRAVITY LIMITS Center-of-Gravity Moment Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-1 WEIGHT AND BALANCE DATA The airplane must be operated in accordance with the approved loading schedule. Refer to Weight and Balance Data Sheet and FAA Approved Model 560 Encore+ Weight and Balance Manual. CERTIFICATION AND OPERATIONAL LIMITATIONS ARE CONDITIONS OF THE TYPE AND AIRWORTHINESS CERTIFICATES AND MUST BE COMPLIED WITH AT ALL TIMES AS REQUIRED BY LAW. 2-3 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration CENTER-OF-GRAVITY LIMITS Figure 2-1 56FMC-00 2-4 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration POWERPLANT LIMITATIONS Engine Type . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pratt and Whitney Canada Inc. PW535B Turbofan Engine starts with ENG CNTL FAULT L/R Illuminated are prohibited. TLD lights must be verified extinguished in preflight check. Refer to NORMAL PROCEDURES, EXTERIOR INSPECTION - Hot Items/Lights. MFD must display valid Engine Indicating System (EIS) information prior to start. Engine Operating Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-2 Inter-Turbine Temperatures Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-3 Engine Overspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-4 Takeoff/Go-Around Thrust (TO Detent). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 4-11 Maximum Continuous Thrust (CLB Detent) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 4-12 Multi-Engine Normal Climb (CLB Detent) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 4-13 ENGINE OPERATING LIMITS * Refer to Figure 2-4. ** Refer to Figure 2-3. Figure 2-2 NOTE 1. Oil Pressure a. Normal oil pressure is 45 to 160 PSI at N 2 speeds above 60%. Oil pressure below 45 PSI is undesirable and should be tolerated only for the completion of the flight, preferably at reduced power setting. b. Oil pressure may be >160 PSI but <270 PSI for up to 400 seconds. 2. Takeoff ratings that are nominally limited to 5 minutes duration: a. May be used for up to 10 minutes for One Engine Inoperative operations without adverse effects on engine airworthiness. b. This is limited to 4 minutes for static operations when the ambient temperature is greater than 86°F (30°C). 3. High Idle corresponds to Flight Idle. OPERATING CONDITION OPERATING LIMITS OIL TEMP o C THRUST SETTING TIME LIMIT MAX OBSERVED ITTo C N 2 % N 1 % OIL PRESSURE (NOTE 1) PSI TAKEOFF 5 MINUTES (NOTE 2) 700 100 100 45 TO 160 10 TO 132.2 MAXIMUM CONTINUOUS CONTINUOUS 700 100 100 45 TO 160 10 TO 132.2 GROUND IDLE CONTINUOUS -- 49.1 MIN -- 25 TO 160 -40 TO 132.2 FLIGHT IDLE (NOTE 3) CONTINUOUS -- 52.9 MIN -- 25 TO 160 -40 TO 132.2 STARTING -- 740** -- -- -- 40 MIN TRANSIENT 20 SECONDS 740** 102* 102* 0 MIN -- TRANSIENT 400 SECONDS (NOTE 1b) -- -- -- 20 TO 270 140.5 MAX 2-5 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration Figure 2-3 56FMC-00 2-6 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration ENGINE OVERSPEED LIMITS Figure 2-4 2-7 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration BATTERY AND STARTER CYCLE LIMITATIONS NOTE 1. If battery limitation is exceeded, a deep cycle including a capacity check must be accomplished to detect possible cell damage. Refer to Chapter 24 of the Maintenance Manual for procedure. 2. Three generator assisted cross starts are equal to one battery start. 3. If an external power unit is used for start, no battery cycle is counted. 4. Use of an external power source with voltage in excess of 28 VDC or current in excess of 1000 amps may damage the starter. Minimum 800 amps for start. GROUND OPERATION Continuous engine ground static operation up to and including five minutes at takeoff thrust is limited to those ambient temperatures shown in Figure 2-7. Limit ground operation of pitot static heat to 2 minutes ON with 2 minutes OFF between cycles to preclude system damage. Electrical load is limited to 125 amps per generator during ground operations at ground idle and 225 amps at high idle. Transients up to 300 amps are permissible for up to 4 minutes. HYDRAULIC FLUID Use Skydrol 500A, B, B-4, C, or LD-4; or Hyjet, Hyjet W, III, IV, IVA or IVA Plus only. APPROVED OILS The following oils are approved for engine use: In addition, oils listed for the engine in the latest revision to Pratt and Whitney Canada Engine Maintenance Manual. CAUTION CAUTION WHEN CHANGING FROM AN EXISTING LUBRICANT FORMULATION TO A “THIRD GENERATION” LUBRICANT FORMULATION (AEROSHELL TURBINE OIL 560 OR MOBIL JET 254), THE ENGINE MANUFACTURER STRONGLY RECOMMENDS THAT SUCH A CHANGE SHOULD ONLY BE MADE WHEN AN ENGINE IS NEW OR FRESHLY OVERHAULED. FOR ADDITIONAL INFORMATION ON USE OF THIRD GENERATION OILS, REFER TO ENGINE MANUFACTURER’S PERTINENT OIL SERVICE BULLETINS. Starter Limitation: Three engine starts per 30 minutes. Three cycles of operation with a 90-second rest period between cycles is permitted. Battery Limitation: Three engine starts per hour. Refer to notes 2 and 3. MOBIL JET OIL II EXXON TURBO OIL 2380 AEROSHELL TURBINE OIL 500 MOBIL JET OIL 254 ROYCO TURBINE OIL 500 AEROSHELL TURBINE OIL 560 CASTROL 5000 ROYCO TURBINE OIL 560 BP TURBO OIL 2380 56FMC-00 2-8 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration Should it be necessary to replenish oil consumption losses when oil of the same brand (as tank contents) is unavailable, then the following requirements apply: For contingency purposes, oil replenishment using any other approved oil brand listed is acceptable provided: 1. The total quantity of added oil does not exceed two U.S. quarts in any 400-hour period. 2. If it is required to add more than two U.S. quarts of dissimilar oil brands, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions. Should oils of nonapproved brands or of different viscosities become intermixed, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions. SINGLE POINT REFUELING LIMITATION Single point refueling operations must be accomplished per the procedures contained on the placard installed on the single point refueling access door. Refueling pressure range is 10 to 50 PSI, maximum defueling pressure is -10 PSI. FUEL LIMITATIONS FUEL BOOST Pumps - ON; when low fuel lights illuminate or at 180 ± 20 pounds or less indicated fuel. The following fuels are approved for use in accordance with Figure 2-6. COMMERCIAL KEROSENE JET A, JET A-1, JET B, JP-4, JP-5 and JP-8. FUEL LIMITATIONS Figure 2-5 Maximum Asymmetrical Fuel Differential for Normal Operations . . . . . . . . . . . . . . . . . . . 200 Pounds NOTE Flight characteristics requirements were not demonstrated with unbalanced fuel above 200 pounds. A lateral fuel imbalance of 600 pounds has been demonstrated for emergency return. FUEL GRADE FUEL SPECIFICATION MINIMUM FUEL TEMPERATURE (TAKEOFF) MAXIMUM FUEL TEMPERATURE (TAKEOFF) MAXIMUM ALTITUDE JET A ASTM-D1655 -35o C +55 o C 45,000 FEET JET A-1 ASTM-D1655 -40o C +55 o C 45,000 FEET JP-5 MIL-DTL-5624 -40o C +55 o C 45,000 FEET JP-8 MIL-DTL-83133 -40oC +55 oC 45,000 FEET 2-9 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration RESERVED FOR FUTURE USE Figure 2-6 56FMC-00 2-10 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration UNUSABLE FUEL Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not usable in flight. SPEED LIMITATIONS Maximum Operating Limit Speeds: MMO (Above 28,907 Feet). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.755 Mach (Indicated) VMO (Between 8000 and 28,907 Feet) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 292 KIAS VMO (Below 8000 Feet). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 262 KIAS The maximum operating limit speeds may not be deliberately exceeded in any phase of flight (climb, cruise or descent) unless a higher speed is authorized for flight test or pilot training. Maximum Maneuvering Speeds - VA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-8 Full application of rudder and aileron controls as well as maneuvers that involve angles-of-attack near the stall should be confined to speeds below maximum maneuvering speed. Maximum Flap Extended Speed - V FE : Full Flaps - LAND Position (35°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 173 KIAS Partial Flaps - T.O. (7°) and T.O. & APPR Position (15°) . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS Maximum Landing Gear Extended Speed - V LE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS Maximum Landing Gear Operating Speed - V LO (Extending). . . . . . . . . . . . . . . . . . . . . 250 KIAS - VLO (Retracting) . . . . . . . . . . . . . . . . . . . . . 200 KIAS Maximum Speed Brake Operation Speed - VSB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . No Limit Minimum Control Speeds (V MCA, VMCL, VMCG ) Refer to Section IV, PERFORMANCE GENERAL Autopilot Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 292 KIAS or 0.755 MACH Minimum Speed For Sustained Flight In Icing Conditions: (Except Approach and Landing) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160 KIAS Minimum Speed in RVSM airspace . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150 KIAS TAKEOFF AND LANDING OPERATIONAL LIMITS Maximum Altitude Limit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,000 Feet Maximum Tailwind Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Knots Maximum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(Refer to Figure 2-7) Minimum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -54°C Maximum Water/Slush on Runway . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .0.5 inches Maximum Tire Ground Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 165 Knots Goodrich/Michelin part number 031-613-8 is the only nose tire approved. The nose tire must be inflated to 125 ±5 PSI. The autopilot and yaw damper must be OFF for takeoff and landing. Takeoff and landings are limited to paved runway surfaces. Takeoff with antiskid inoperative is prohibited. The nosewheel must be in firm contact with the ground prior to extending speed brakes and/or deploying thrust reversers. Pulselight system operation within 300 feet AGL on landing approach is prohibited. (Continued Next Page) 2-11 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration TAKEOFF AND LANDING OPERATIONAL LIMITS (Continued) Takeoff is prohibited with the following forms of contamination: 1. With frost adhering to the following critical areas: • Wing Leading Edge • Upper Wing Surface • Windshield 2. With ice, snow or slush adhering to the following critical areas: • Wing Leading Edge and Upper Wing Surface • Flight Control Surfaces including all hinge gaps • Horizontal Stabilizer • Vertical Stabilizer • Engine Inlets • Top of Engine Pylons • Top of Fuselage • Windshield • All Static Ports • Angle of Attack Vanes • Upper surface of nose forward of the windshield NOTE Refer to Section VII for information regarding Ground Deicing and Anti-icing procedures. 3. A visual and tactile (hand on surface) check of the wing leading edge and wing upper surface must be performed to ensure the wing is free from frost, ice, snow, or slush when the outside air temperature is less than 10°C (50°F) or if it cannot be determined that the wing fuel temperature is above 0°C (32°F) and any of the following conditions exist: a. There is visible moisture present (rain, drizzle, sleet, snow, fog, etc.); or b. Water is present on the wing upper surface; or c. The difference between dew point and outside temperature is 3°C (5°F) or less; or d. The atmospheric conditions have been conducive to frost formation. ICE AND RAIN PROTECTION In icing conditions, the airplane must be operated, and its ice protection systems must be used, as described in Section III, Normal Procedures, ANTI-ICE SYSTEMS. Specific operational speeds and performance information must be used where established for such conditions. The anti-ice switches should be selected WING/ENGINE ON when operating in visible moisture, and the indicated RAT is +10°C (+50°F) or below. Tail deice should be turned on when in visible moisture and the indicated RAT is between +10°C (+50°F) and -35°C (-31°F)/-40°C (-40°F) as applicable. Limit the ground operation of the pitot-static heat to two minutes to preclude damage to the pitot tubes and angle-of-attack vanes. Anti-ice systems must not be used to deice surfaces prior to takeoff. CAUTION CAUTION TO PREVENT POSSIBLE ENGINE DAMAGE FROM INGESTION OF ICE, DO NOT CHIP OR SCRAPE ICE OR SNOW FROM THE ENGINE AIR INLET. DEICE THESE AREAS PRIOR TO START (REFER TO SECTION VII, ADVISORY INFORMATION, GROUND DEICE/ANTI-ICE OPERATIONS). 56FMC-00 2-12 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration ICE AND RAIN PROTECTION (Continued) Minimum airspeed for sustained flight in icing (except approach and landing) is 160 KIAS. In icing conditions, operating the airplane at other than flaps 0° for an extended period of time (except approach and landing) is prohibited. OPERATIONS IN SEVERE ICING CONDITIONS WARNING SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIRPLANE IS CERTIFIED. FLIGHT IN FREEZING RAIN, FREEZING DRIZZLE, OR MIXED ICING CONDITIONS (SUPERCOOLED LIQUID WATER AND ICE CRYSTALS) MAY RESULT IN I C E B U I L D - U P O N P R O T E C T E D S U R FA C E S E X C E E D I N G T H E CAPABILITY OF THE ICE PROTECTION SYSTEM, OR MAY RESULT IN ICE FORMING AFT OF THE PROTECTED SURFACES. THIS ICE MAY NOT BE SHED WHEN USING THE ICE PROTECTION SYSTEMS, AND MAY SERIOUSLY DEGRADE THE PERFORMANCE AND CONTROLLABILITY OF THE AIRPLANE. RUNBACK ICE EXTENDING APPROXIMATELY 12 TO 18 INCHES AFT OF THE HEATED LEADING EDGE ON THE UPPER SURFACE OF THE WING IS NORMAL IN SOME ICING CONDITIONS, HAS BEEN EVALUATED TO ENSURE SATISFACTORY PERFORMANCE AND CONTROLLABILITY, AND IS NOT AN INDICATION OF SEVERE ICING. During flight, severe icing conditions that exceed those for which the airplane is certified shall be determined by the following visual cues: 1. Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice. 2. Accumulation of ice on the upper surface of the wing aft of the protected area extending more than 12 to 18 inches aft of the heated leading edge. NOTE The outboard 32 inches of each wing is unheated and ice will accumumlate with the wing anti-ice operating normally. If one or more of these visual cues exist, immediately request priority handling from Air Traffic Control to facilitate a route or altitude change to exit the icing environment. PERFORMANCE CONFIGURATION The airplane configuration must be as presented under Standard Performance Conditions, Section IV, Performance. ENROUTE OPERATIONAL LIMITS Maximum Operating Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45,000 Feet Maximum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-7 Minimum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-7 Generator Load (Above Idle) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 Amperes in Flight Generator Load (Idle) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 225 Amperes in Flight 2-13 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration OPERATIONS AUTHORIZED This airplane is approved for day and night, VFR, IFR flight and flight into known icing conditions. This airplane is not approved for ditching under 14 CFR Part 25.801. BOUNDARY LAYER ENERGIZERS All boundary layer energizers must be present for dispatch (16 per wing). MINIMUM CREW Minimum Flight Crew for All Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Pilot and 1 Copilot Figure 2-7 TAKEOFF/LANDING/ENROUTE TEMPERATURE LIMITATIONS 56FMC-00 2-14 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration WARNING AV OID RAPID AND LARGE ALTERNAT ING CONTROL INPUTS, ESPECIALLY IN COMBINATION WITH LARGE CHANGES IN PITCH, ROLL, OR YAW (E.G. LARGE SIDESLIP ANGLE), AS THEY MAY RESULT IN STRUCTURAL FAILURES AT ANY SPEED, INCLUDING BELOW VA. MAXIMUM MANEUVERING SPEEDS EXAMPLE: PRESSURE ALTITUDE - 25,000 FEET WEIGHT - 16,830 POUNDS MAXIMUM MANEUVERING SPEED - 236 KNOTS Figure 2-8 2-15 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration LOAD FACTOR In Flight Flaps UP Position (0°). . . . . . . . . . . . . . . . . . . . . . . . . . . . . -1.44 to +3.6G at 16,830 Pounds Flaps T.O., T.O. & APPR and LAND Position (7° To 35°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.0 to +2.0G at 16,830 Pounds NOTE These accelerations limit the angle-of-bank in turns and limit the severity of pull-up/ push-over maneuvers. Landing Flaps LAND Position (35°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +3.46G at 15,200 Pounds NOTE This acceleration limits the airplane to a maximum landing sink rate of 600 feet-per- minute. CABIN PRESSURIZATION LIMITATIONS Normal Cabin Pressurization Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.0 to 9.0 PSI Differential Airplane must be depressurized for takeoff and landing. MANEUVERS No acrobatic maneuvers, including spins, are approved. No intentional stalls permitted above 25,000 feet. PASSENGER COMPARTMENT For all takeoff and landings, seats must be fully upright and outboard. The seat just aft of the emergency exit must be to the most aft position (toward rear of airplane) and passenger seat belts and shoulder harnesses must be fastened. Maximum number of passenger seats is 11. ANGLE-OF-ATTACK/STICK SHAKER SYSTEM The angle-of-attack system may be used as a reference system but does not replace the airspeed display in the PFD as a primary instrument. The angle-of-attack system can be used as a reference for approach speed (1.3 VS1 ) at all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing flap positions. 1.3 V S1 is indicated by approximately .6 on the AOA gage and by the green circle on the pilot’s and copilot’s PFD airspeed tapes. The angle-of-attack and stall warning system must be operable and a satisfactory preflight test must be performed in accordance with Section III, Normal Procedures. AIRPLANE BATTERY If the BATT O’TEMP light illuminates during ground operation, do not takeoff until after the proper maintenance procedures have been accomplished. 56FMC-00 2-16 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration INSTRUMENT MARKINGS NOTE Digital readout is displayed only when temperature is outside normal operating limits. Digit color will match pointer color. (Continued Next Page) FAN (N 1) RPM INDICATORS Scale Markings Red Line 102.1% RPM Yellow Band 100.1 - 102.0% RPM Tape/Pointer/Digital Readout Red >102.1% RPM or 100.1 - 102.0% RPM for more than 20 seconds Tape/Pointer White <100.0% RPM or 100.1 - 102.0% RPM for less than 20 seconds Digital Readout Green <100.0% RPM or 100.1 - 102.0% RPM for less than 20 seconds INTER-TURBINE TEMPERATURE INDICATORS Engine Start Scale Markings Red Line 741°C Yellow Band 701 - 740°C Tape/Pointer Red >741°C or 701 - 740°C for more than 5-7 seconds (see figure 2-3) White <700°C or 701 - 740°C for less than 5-7 seconds (see figure 2-3) INTER-TURBINE TEMPERATURE INDICATORS Engine Running (Non-Start) Scale Markings Red Line 741°C Yellow Band 701 - 740°C Tape/Pointer Red >741°C or 701 - 740°C for more than 20 seconds White <700°C or 701 - 740°C for less than 20 seconds OIL TEMPERATURE INDICATORS Scale Markings Red Band >140°C and < -40°C Yellow Band >132°C - <140°C and < +10°C to > - 40°C Green Band >10°C - <132°C Pointer Red >140°C or >132°C - <140°C for more than 200 seconds or < -40°C Yellow >132°C - <140°C for less than 200 seconds or < +10°C to > - 40°C Green >10°C - <132°C 2-17 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration INSTRUMENT MARKINGS (Continued) NOTE • Digital readout is displayed only when pressure is outside normal operating limits. Digit color will match pointer color. (Continued Next Page) TURBINE (N 2 ) RPM INDICATORS Digital Readout Red >102.1% RPM or 100.1 - 102.0% for more than 20 seconds Green <100.0% RPM or 100.1 - 102.0% for less than 20 seconds OIL PRESSURE INDICATORS Scale Markings Red >270 and <25 Yellow >160 - <270 and >25 - <45 Green >45 - <160 Pointer (N2 >60%) Red <25 or >25 - <45 for more than 400 seconds or >270 or >160 - <270 for more than 400 seconds Yellow > 2 5 - < 4 5 f o r l e s s t h a n 4 0 0 seconds or >160 - <270 for less than 400 seconds Green >45 - <160 Pointer (N2 <60%) Red <25 or >270 or >160 - <270 for more than 400 seconds Yellow >160 - <270 for less than 400 seconds Green >25 - <160 AIRSPEED INDICATOR MARKING SIGNIFICANCE AIRSPEED Red Line VMCA 86 KIAS Green Circle 1.3VS1 VREF Red Marker (These speeds may not be deliberately exceeded in any flight regime) VMO 262 KIAS (Sea Level - 8,000 feet) VMO 292 KIAS (Above 8,000 - 28,907 feet) MMO 0.755 Mach (Above 28,907) Top of Low Speed Cue (LSC) Stick Shaker/ Impending Stall Speed Function of Weight 56FMC-00 2-18 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration INSTRUMENT MARKINGS (Continued) LEFT AND RIGHT AMMETER INDICATORS Red Line: 300 Amps CABIN DIFFERENTIAL PRESSURE INDICATOR Red Line: 9.0 PSI Green Arc: 0.0 to 8.9 PSI OXYGEN PRESSURE INDICATOR Red Line: 2000 PSI Yellow Arc: 0.0 to 400 PSI Green Arc: 1600 to 1800 PSI BRAKE AND GEAR PNEUMATIC PRESSURE INDICATOR (IN NOSE COMPARTMENT) Narrow Red Arc: 0-1600 PSI Wide Yellow Arc: 1600 to 1800 PSI Wide Green Arc: 1800 to 2050 PSI Wide Red Arc: Above 2050 PSI BRAKE HYDRAULIC ACCUMULATOR PRESSURE INDICATOR (IN NOSE COMPARTMENT) Red Arc: <675 PSI Grey Band: 675 PSI Yellow Arc: > 675 to 1100 PSI Green Arc: >1100 to 1500 PSI Red Arc: >1500 PSI ANGLE OF ATTACK INDICATOR White Band: 0.57 to 0.63 Yellow Arc: 0.63 to 0.84 Red Arc: 0.84 to 1.00 BATTERY TEMPERATURE INDICATOR Yellow Arc: 145 to 160 Red Arc: 160 to 180 2-19 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration AUTOPILOT 1. One pilot must remain in his seat with the seat belt fastened during all autopilot operations. 2. The FCS-3000 system must be verified to be operational by a satisfactory automatic preflight test (no messages on power up) prior to each flight in which the autopilot is to be used. 3. The autopilot minimum engage height, during climb following takeoff or go-around, is 300 feet AGL. 4. The autopilot minimum use height is: a. ILS Approach (CAT I) 90 Feet AGL. b. LNAV/VNAV Approach with a DA 200 Feet AGL. c. Non-precision Approaches 200 Feet AGL. d. Cruise 1000 Feet AGL. 5. Do not overide the autopilot in pitch. NOTE Overriding the autopilot in pitch does not cancel the autopilot automatic trim. If a force is applied to the column with the autopilot engaged, then automatic trim will run to oppose the applied force. This can lead to a severe out-of-trim condition during any phase of flight. 6. Operation of the autopilot with a pitch trim malfunction is prohibited. ROCKWELL COLLINS FCS-3000 INTEGRATED FLIGHT CONTROL SYSTEM The Rockwell Collins Pro Line 21 Avionics System for Cessna Citation Encore+ Publication Number 523-0808124, dated 1 August 2006 or later applicable revision, must be immediately available to the flight crew. 1. Operating in the composite mode is limited to training and display failure conditions. 2. The pilot's PFD, copilot's PFD and MFD must be installed and operational in the normal mode for takeoff. 3. Category II approaches are not approved. 4. VOR approaches must be conducted in the APPR mode. 5. VOR approaches conducted without DME must be intercepted greater than 6 nautical miles from the VOR. 6. It is prohibited to display the non-coupled side Flight Director unless the coupled side Flight Director is being displayed. Failure to adhere to this limitation will result in incorrect Flight Director guidance. Use of the coupled side Flight Director by itself will operate correctly. 7. Nav and localizer captures must be accomplished with an intercept angle of less than 90°. 8. AHRS 1 and AHRS 2 must be operational for takeoff. 9. ADC 1 and ADC 2 must be operational for takeoff. STANDBY FLIGHT DISPLAY 1. A satisfactory preflight test must be accomplished on the standby flight display using the test in the cockpit preparation check in Section III, Normal Procedures. 2. The standby flight display must be functioning prior to takeoff. 3. The GH-3000 Pilot’s guide part number 501-1741-XX02, copyright 1999 or later applicable revision must be immediately available to the flight crew. 56FMC-00 2-20 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration SUPPLEMENTAL OXYGEN SYSTEM The following aircraft certification requirements are in addition to the requirements of applicable operating rules. The most restrictive requirements (certification or operating) must be observed: Crew and passenger oxygen masks are not approved for use above 40,000 feet cabin altitude. Prolonged operation of passenger masks above 25,000 feet cabin altitudes is not recommended. NOTE Passenger masks are intended for use during an emergency descent to an altitude not requiring supplemental oxygen. The pressure demand crew oxygen masks must be properly stowed in their containers to qualify as a quick-donning oxygen mask. NOTE Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. Cabin temperature must be at or above 0°C (+32°F) for a minimum of 15 minutes prior to flight above FL250 after a prolonged ground cold soak period (two hours or longer) at ambient temperatures of -10°C (+14°F) or colder (refer to Normal Procedures, Cold Weather Operations). This temperature ensures proper deployment and operation of the passenger oxygen masks. HIGH FREQUENCY (HF), AUTOMATIC DIRECTION FINDER (ADF) SYSTEMS The ADF bearing information may be erratic when keying the HF transmitter. Should this occur, disregard the ADF bearing during periods of transmission. THRUST REVERSERS Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on landing roll. The FADEC will limit reverse thrust to a maximum of 2106 lbs. However, in the event of a FADEC fault, the pilot should not exceed 71.4% N1 . Maximum allowable thrust reverser deployed time is 3 minutes in any 10 minute period. Engine static ground operation is limited to idle power (if thrust reversers are deployed). Use of thrust reversers is prohibited during touch and go landings. On the first flight of the day and the first flight after any maintenance action has been performed on the aircraft, the thrust reverser(s) must be verified to be operational by the Before Takeoff test in Section III Normal Procedures. The use of thrust reversers to back the airplane is prohibited. 2-21 56FMC-00 AA MODEL 560 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration GND IDLE SWITCH The GND IDLE switch must be in HIGH position when conducting touch and go landings. TAIL DEICE SYSTEM Minimum Temperature for use (Airspeed below 150 KIAS) . . . . . . . . . . . . . . . . . . -40°C (-40°F) RAT Minimum Temperature for use (Airspeed at or above 150 KIAS) . . . . . . . . . . . . . . -35°C (-31°F) RAT CAUTION CAUTION DO NOT OPERATE DEICE BOOTS UNDER ANY OF THE FOLLOWING CONDITIONS BECAUSE BOOT CRACKING MAY RESULT: • AIRSPEEDS AT OR ABOVE 150 KIAS AND THE RAT IS LESS THAN OR EQUAL TO -35°C (-31°F). • AIRSPEEDS BELOW 150 KIAS AND THE RAT IS LESS THAN OR EQUAL TO -40°C (-40°F). 56FMC-00 2-22 AA MODEL 560 SECTION III - OPERATING PROCEDURES GENERAL FAA APPROVED U.S. Configuration OPERATING PROCEDURES TABLE OF CONTENTS PAGE OPERATING PROCEDURES - GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3/3-4 Warning/Caution/Advisory Light System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3/3-4 EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 ABNORMAL PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-35 NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-71 3-1/3-2 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES GENERAL FAA APPROVED U.S. Configuration OPERATING PROCEDURES - GENERAL The operating procedures contained in this manual have been developed and recommended by Cessna Aircraft Company and are approved by the FAA for use in the operation of this airplane. This section contains the emergency, abnormal and normal procedures for your airplane. For your convenience, definitions of these terms are listed in Section I. Some emergency situations require immediate corrective action. These numbered steps are printed in boxes in the emergency procedures and should be done without the aid of the checklist. WARNING/CAUTION/ADVISORY LIGHT SYSTEM Annunciator lights are classified as WARNING, CAUTION, and ADVISORY. All except those associated with the Electronic Flight Instrument System (EFIS), autopilot, avionics, and engine fire warning/suppression systems are located in the annunciator panel. The abnormal and emergency procedures in this section are keyed, where applicable, to these annunciators. Warning lights are generally red (except failure of both generators). Illumination of warning lights in the annunciator panel will cause both MASTER WARNING RESET lights to flash. Failure of both generators (amber annunciators) is considered a red function and triggers the MASTER WARNING. Illumination of the LH/RH ENGINE FIRE light(s) will not trigger the MASTER WARNING lights. CAUTION lights are amber. Illumination of caution lights, located in the annunciator panel, will cause both MASTER CAUTION RESET lights to illuminate. Some annunciators have time delays before illuminating the MASTER CAUTION. Some pilot selected functions such as fuel crossfeed (causing the fuel boost pumps to come on), will not activate the MASTER CAUTION. When a red annunciator illuminates, it will flash until the MASTER WARNING is reset by pushing the MASTER WARNING RESET light. If the condition which caused the annunciator to illuminate is corrected prior to resetting the MASTER WARNING, the annunciator will extinguish, but the MASTER WARNING will continue to flash until reset. When a yellow annunciator illuminates, it will flash until the MASTER CAUTION is reset by pushing the MASTER CAUTION RESET light. If the condition which caused the annunciator to illuminate is corrected prior to resetting the MASTER CAUTION, the annunciator and MASTER CAUTION will extinguish. ADVISORY lights are white and do not trigger a master warning or master caution. When an advisory light is illuminated, pilot action may be required. If an action is required it will be in the ABNORMAL PROCEDURES in this section. 3-3/3-4 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration EMERGENCY PROCEDURES TABLE OF CONTENTS PAGE EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 ENGINE Engine Failure or Fire, or Master Warning During Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Engine Fire (LH or RH Engine Fire Warning Light On) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Engine Failure During Final Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Emergency Restart - Two Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9 Maximum Glide - Emergency Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9 Airstart Envelope. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-10 High Oil Pressure Indication (Red Pointer and Digits) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 Low Oil Pressure Indication (Red Pointer and Digits) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 Low Oil Pressure (LO OIL PRESS L or R Warning Light On) . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 HYDRAULICS/BRAKES Thrust Reverser Inadvertent Deployment During Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 Thrust Reverser Inadvertent Inflight Deployment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13 Thrust Reverser Unlock Light On In Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15 Thrust Reverser Arm Light On In Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15 ENVIRONMENTAL/PRESSURIZATION Overpressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 Cabin Decompression (CAB ALT Warning Light On) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 Cabin Pressurization Controller Failure (Red LED Illuminated) . . . . . . . . . . . . . . . . . . . . . . . 3-18 Emergency Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-18 Environmental System Smoke or Odor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-19 Smoke Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-20 ELECTRICAL Electrical Fire or Smoke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-21 Battery Overtemperature (BATT O’TEMP Warning Light On). . . . . . . . . . . . . . . . . . . . . . . . . 3-23 Loss of Both Generators (Gen Off L and R Caution Lights On and Master Warning). . . . . . . . . . . . . . . . . . . . . . . . . . . 3-24 FLIGHT GUIDANCE Autopilot Malfunction. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-25 Autopilot Out Of Trim (RED BOXED “EK,L,” or “AI,J” ON PFD’s) . . . . . . . . . . . . . . . . . . . . 3-25 PFD Attitude Failure - Single (Amber AP, Red ATT and White XAHS Displayed On One PFD) . 3-26 PFD Attitude Failure - Dual ((Amber AP, Red ATT, and White XAHS on both PFD’S) . . . . . . 3-26 PFD Heading Failure - Single (Amber AP, Red HDG and White XAHS Displayed On One PFD) 3-26 PFD Heading Failure - Dual (Amber AP, Red HDG, and White XAHS on both PFD’S) . . . . . 3-26 Air Data Computer Failure - Single (Red IAS/ALT/VS Displayed On One PFD). . . . . . . . . . . 3-27 Air Data Computer Failure - Dual (Red IAS/ALT/VS on both PFD’S) . . . . . . . . . . . . . . . . . . . 3-27 Red Boxed FD Displayed on PFD (Flight Guidance Computer Failure) . . . . . . . . . . . . . . . . . 3-27 Red AOA1 or AOA2 Displayed on PFD (Low Speed Cue (LSC) AOA Failure) . . . . . . . . . . . 3-28 Red DCP 1 or DCP 2 Displayed on PFD (Display Control Panel Failure) . . . . . . . . . . . . . . . 3-28 Electric Elevator Runaway Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-29 (Continued Next Page) 3-5 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration TABLE OF CONTENTS (Continued) PAGE EVACUATION Emergency Evacuation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-29 Ditching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-30 56FMC-00 3-6 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration EMERGENCY PROCEDURES ENGINE FAILURE OR FIRE, OR MASTER WARNING DURING TAKEOFF . • Brakes - AS REQUIRED. • Throttles - IDLE. • Speed Brakes - EXTEND. • Thrust Reverser - DEPLOY ON UNAFFECTED ENGINE. 1. Thrust Reverser Indicator Lights - CHECK ILLUMINATION of ARM, UNLOCK AND DEPLOY LIGHTS. 2. Thrust Reverser - REVERSE THRUST ON THE UNAFFECTED ENGINE. 3. Thrust Reverser - REVERSE LEVER TO IDLE REVERSE AT 60 KIAS. NOTE • To obtain maximum braking performance from the antiskid system, the pilot must apply continuous maximum effort (no modulation) to the brake pedals. • The Takeoff Field Lengths assume that the pilot has maximum effort applied to the brakes at the scheduled V1 speed during the aborted takeoff. 4. When airplane comes to a stop - Refer to Emergency Procedures, EMERGENCY EVACUATION (if appropriate). • Rotate - VR. • Landing Gear - UP (after positive rate-of-climb). • Climb - V 2 until Level Off Altitude. 1. Flaps - RETRACT at Level Off Altitude and V2 + 10 KIAS, accelerate to VENR (160 KIAS). IF ENGINE FIRE 2. At or above 400 feet AGL, Accomplish Emergency Procedures, ENGINE FIRE. IF ENGINE FAILURE 2. At or above 400 feet AGL, Accomplish Abnormal Procedures, IN-FLIGHT RESTART - ONE ENGINE or Abnormal Procedures, ENGINE FAILURE/PRECAUTIONARY SHUTDOWN. SPEED BELOW V1 - TAKEOFF ABORTED SPEED ABOVE V1 - TAKEOFF CONTINUED 3-7 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration ENGINE FIRE (LH OR RH ENGINE FIRE WARNING LIGHT ON) 4. Throttle (affected engine) - OFF. 5. Electrical Load - REDUCE as required. 6. Affected ENGINE Anti-ice - CHECK OFF. 7. WING XFLOW Switch - ON as required. IF FIRE WARNING LIGHT REMAINS ON AFTER 30 SECONDS 8. Remaining Illuminated BOTTLE ARMED Light - PUSH. 9. Land as soon as possible. 10. Refer to Abnormal Procedures, SINGLE-ENGINE APPROACH and LANDING. IF LIGHT GOES OUT AND SECONDARY INDICATIONS ARE NOT PRESENT 2. Land as soon as practical. 3. Refer to Abnormal Procedures, SINGLE-ENGINE APPROACH and LANDING. ENGINE FAILURE DURING FINAL APPROACH 4. Rudder and Aileron Trim - TRIM toward operating engine as required. 5. Multiply Flaps 35° landing distance by 1.4. 6. Passenger Advisory Lights - PASS SAFETY. 7. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure. 8. Exterior Lights - AS REQUIRED. 9. Fuel CROSSFEED Switch - OFF. 10. Annunciators - CHECK. 11. GND IDLE Switch - NORM. 12. Pressurization - CHECK ZERO DIFFERENTIAL PRIOR TO LANDING. 13. Landing Gear - DOWN. 14. Flap Override Switch - GPWS FLAP OVRD ON (amber). 15. ANTI-SKID Switch - CHECK ON. 16. Landing Lights - AS DESIRED. 17. Autopilot and Yaw Damper - OFF. 18. Speed Brakes - RETRACT (50 feet AGL and below). 1. Throttle (affected engine) - IDLE. IF LIGHT REMAINS ON (15 SECONDS) PROBABLE FIRE 2. ENGINE FIRE Switch (affected engine) - LIFT COVER and PUSH. 3. Either Illuminated BOTTLE ARMED Light - PUSH. 1. Thrust (operating engine) - INCREASE as required. 2. Airspeed - VAPP. 3. Flaps - T.O. & APPR (15°). 56FMC-00 3-8 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration EMERGENCY RESTART - TWO ENGINES 3. If altitude allows - INCREASE AIRSPEED to 200 KIAS. 4. ENGINE FIRE Switches - CHECK OPEN (F/W SHUTOFF Caution Light L or R extinguished). 5. All Anti-Ice Switches - OFF. IF NO START IN TEN SECONDS 6. Either ENGINE START Button - PRESS momentarily. IF ENGINE DOES NOT START 7. ENGINE START DISENGAGE Button - PRESS momentarily. 8. ENGINE START Button - (Other engine) PRESS momentarily. IF ENGINE DOES NOT START 9. ENGINE START DISENGAGE Button - PRESS momentarily. 10. Refer to Emergency Procedures, MAXIMUM GLIDE - EMERGENCY LANDING. IF FIRST ENGINE STARTS 7. Thrust (operating engine) - INCREASE to arrest descent. 8. ENGINE START BUTTON (other engine) - PRESS momentarily. IF ONLY ONE ENGINE RESTARTS 9. Refer to Abnormal Procedures, SINGLE ENGINE APPROACH AND LANDING. 10. Land as soon as practical. IF BOTH ENGINES RESTART 9. Land as soon as practical. MAXIMUM GLIDE - EMERGENCY LANDING 1. Airspeed - Per Chart Below. NOTE The speed brakes and flaps may not operate. If flap lever is moved, the flaps may tend to float in a trail position. Landing gear extension, if required, must follow emergency gear release procedures. 2. Flaps - UP. 3. Flap Override Switch - GPWS FLAP OVRD ON (amber). 4. Speed Brakes - RETRACT. 5. ATC - ADVISE. 6. Transponder - EMERGENCY. 7. Passenger Advisory Lights - PASS SAFETY. 8. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure, and stow loose items securely. 9. Shoulder Harnesses - SECURE. 10. Landing Gear - AS DESIRED prior to touchdown. 1. FUEL BOOST Pumps - BOTH ON. 2. Throttles - CUTOFF, then IDLE. AIRSPEED FOR MAXIMUM RANGE GLIDE (NO WIND) WEIGHT (POUNDS) 11,000 12,000 13,000 14,000 15,000 16,000 16,830 KIAS 111 116 120 125 129 133 137 3-9 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration AIRSTART ENVELOPE Figure 3-1 3-10 AA 56FMC-00 MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration HIGH OIL PRESSURE INDICATION (RED POINTER AND DIGITS) 1. Throttle (affected engine) - REDUCE THRUST. 2. Land as soon as practical. LOW OIL PRESSURE INDICATION (RED POINTER AND DIGITS) 1. Throttle (Affected Engine) - REDUCE THRUST (below 60% N2). IF POINTER AND DIGITS INDICATE ZERO AND LOW OIL PRESSURE ANNUNCIATION NOT ILLUMINATED 2. DCU PRI and DCU SEC circuit breaker (affected side panel) - CHECK. IF POINTER AND DIGITS CHANGE TO AMBER OR GREEN 2. Throttle (Affected Engine) - MAINTAIN below 60% N2. 3. Land as soon as practical. IF POINTER AND DIGITS REMAIN RED OR RETURN TO RED 2. Throttle (Affected Engine) - OFF. 3. Refer to Abnormal Procedures, ENGINE FAILURE/PRECAUTIONARY SHUTDOWN. LOW OIL PRESSURE (LO OIL PRESS L OR R WARNING LIGHT ON) Indicates oil pressure at the warning transducer is 20 PSI or less. 1. Throttle (Affected Engine) - REDUCE. IF OIL PRESSURE INDICATION DOES NOT RESPOND TO THROTTLE MOVEMENT OR POINTER TURNS RED 2. Throttle (Affected Engine) - OFF. 3. Refer to Abnormal Procedures, ENGINE FAILURE/PRECAUTIONARY SHUTDOWN. IF OIL PRESSURE INDICATION RESPONDS TO THROTTLE MOVEMENT AND POINTER REMAINS GREEN 2. Throttle (Affected Engine) - IDLE or AS REQUIRED. 3. Monitor EIS oil pressure indication. 4. Land as soon as practical. THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF • Brakes - AS REQUIRED. • Throttles - IDLE. • Speed Brakes - EXTEND. • Thrust Reversers - BOTH DEPLOY. 1. Thrust Reverser Indicator Lights - CHECK ILLUMINATION of ARM, UNLOCK and DEPLOY LIGHTS. 2. Thrust Reversers - REVERSE THRUST ON BOTH ENGINES. (Continued Next Page) SPEED BELOW V1 - TAKEOFF ABORTED 3-11 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued) . • Rotate - V R. • Landing Gear - UP (after positive rate-of-climb). Do not exceed 150 KIAS until thrust reverser stows. • Climb Airspeed - V2 . IF THRUST REVERSER STOWS 2. Thrust Reverser Indicator Lights - CHECK UNLOCK and DEPLOY LIGHT EXTINGUISHED. - ARM LIGHT ILLUMINATED. 3. Throttle (affected engine) - IDLE, then AS REQUIRED. 4. Flaps - RETRACT at V2 +10 KIAS and accelerate. 5. Airspeed - MAINTAIN 200 KIAS or below (after T/R stows). 6. Altitude - FL310 or below. 7. Land as soon as practical (affected thrust reverser will be inoperative). IF THRUST REVERSER WILL NOT STOW WARNING DO NOT ADVANCE THE THROTTLE ON THE AFFECTED ENGINE. REVERSE THRUST WILL INCREASE AFTER THE THROTTLE HAS BEEN BROUGHT TO IDLE AND THEN ADVANCED. 2. THRUST REVERSER Circuit Breaker (LH panel) - CHECK IN. 3. Throttle (affected engine) - OFF. 4. Airspeed - MAINTAIN 150 KIAS or below. 5. Land as soon as possible (affected thrust reverser will be inoperative). 6. Rudder and Aileron Trim - Trim toward operating engine as required. 7. GEN Switch (affected engine) - OFF. 7. Electrical Load - REDUCE as required. 8. Fuel CROSSFEED Switch - AS REQUIRED (maximum imbalance 200 lbs). 10. ENGINE Anti-Ice (affected engine) - CHECK OFF. 11. WING XFLOW Switch - ON as required. WARNING DO NOT USE THE AUTOPILOT OR YAW DAMPER. NOTE If possible, choose a runway with least possible crosswind. BEFORE LANDING (WITH THRUST REVERSER DEPLOYED) 12. Landing Data - COMPUTE and SET. a. Airspeed - VAPP. b. Landing Distance - Multiply landing distance by 1.4 for flaps 15°. 13. Crew Briefing - COMPLETE. 14. Avionics and Flight Instruments - CHECK and SET. (Continued Next Page) SPEED ABOVE V1 - TAKEOFF CONTINUED 1. Emergency STOW Switch (affected engine) - EMER. 56FMC-00 3-12 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued) BEFORE LANDING (WITH THRUST REVERSER DEPLOYED) (Continued) 15. Passenger Advisory Lights - PASS SAFETY. 16. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure. 17. Flaps - T.O. & APPR (15°). 18. Flap Override Switch - GPWS FLAP OVRD ON (amber). 19. Exterior Lights - AS REQUIRED. 20. Fuel CROSSFEED Switch - OFF. 21. Annunciators - CHECK. 22. GND IDLE Switch - NORM. 23. Pressurization - CHECK ZERO DIFFERENTIAL PRIOR TO LANDING. 24. Landing Gear - DOWN. 25. ANTI-SKID Switch - CHECK ON. 26. Landing Lights - AS DESIRED. 27. Airspeed - VAPP. 28. Speed Brakes - RETRACT (50 feet AGL and below). WARNING DO NOT INITIATE GO-AROUND BELOW 600 FEET AGL WITH A THRUST REVERSER DEPLOYED. GO-AROUND (WITH THRUST REVERSER DEPLOYED) 29. Throttle (operating engine) - TO Detent. 30. Airplane Pitch Attitude - +5°. 31. Climb Airspeed - VAPP +10 KIAS. 32. Flaps - 0° (when VAPP +10 KIAS). 33. Landing Gear - UP (when positive rate established). 34. Throttle (operating engine) - CLB Detent (when clear of obstacles). THRUST REVERSER INADVERTENT INFLIGHT DEPLOYMENT 4. THRUST REVERSER Circuit Breaker (LH Panel) - CHECK IN. IF THRUST REVERSER STOWS 5. Thrust Reverser Indicator Lights -CHECK UNLOCK and DEPLOY LIGHT EXTINGUISHED. - ARM LIGHT ILLUMINATED. 6. Throttle (affected engine) - IDLE, then AS REQUIRED. 7. Airspeed - MAINTAIN 200 KIAS or below (after T/R stows). 8. Altitude - FL310 or below. 9. Land as soon as practical (affected thrust reverser will be inoperative). IF THRUST REVERSER WILL NOT STOW 5. Throttle (affected engine) - OFF. (Continued Next Page) 1. Control Wheel/AP TRIM DISC Button - GRIP/PRESS and RELEASE. 2. Emergency STOW Switch (affected engine) - EMER. 3. Airspeed - REDUCE TO 150 KIAS or below. 3-13 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration THRUST REVERSER INADVERTENT INFLIGHT DEPLOYMENT (Continued) IF THRUST REVERSER WILL NOT STOW (Continued) 6. Airspeed - MAINTAIN 150 KIAS or below. 7. Land as soon as possible (affected thrust reverser will be inoperative). 8. Rudder and Aileron Trim - Trim toward operating engine as required. 9. GEN Switch (affected engine) - OFF. 10. Electrical Load - REDUCE as required. 11. Fuel CROSSFEED Switch - AS REQUIRED (maximum imbalance 200 lbs). 12. ENGINE Anti-Ice (affected engine) - CHECK OFF. 13. WING XFLOW Switch - ON as required. WARNING DO NOT USE THE AUTOPILOT OR YAW DAMPER. NOTE If possible, the runway used for landing should have a minimum crosswind. BEFORE LANDING (WITH THRUST REVERSER DEPLOYED) 14. Landing Data - COMPUTE and SET. a. Airspeed - VAPP. b. Landing Distance - Multiply landing distance by 1.4 for flaps 15°. 15. Crew Briefing - COMPLETE. 16. Avionics and Flight Instruments - CHECK and SET. 17. Passenger Advisory Lights - PASS SAFETY. 18. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure. 19. Flaps - T.O. & APPR (15°). 20. Flap Override Switch - GPWS FLAP OVRD ON (amber). 21. Exterior Lights - AS REQUIRED. 22. Fuel CROSSFEED Switch - OFF. 23. Annunciators - CHECK. 24. GND IDLE Switch - NORM. 25. Pressurization - CHECK ZERO DIFFERENTIAL PRIOR TO LANDING. 26. Landing Gear - DOWN. 27. ANTI-SKID Switch - CHECK ON. 28. Landing Lights - AS DESIRED. 29. Airspeed - VAPP. 30. Speed Brakes - RETRACT (50 feet AGL and below). WARNING DO NOT INITIATE GO-AROUND BELOW 600 FEET AGL WITH A THRUST REVERSER DEPLOYED. GO-AROUND (WITH THRUST REVERSER DEPLOYED) 31. Throttle (operating engine) - TO Detent. 32. Airplane Pitch Attitude - +5°. 33. Climb Airspeed - VAPP +10 KIAS. 34. Flaps - 0° (when VAPP +10 KIAS). 35. Landing Gear - UP (when positive rate established). 36. Throttle (operating engine) - CLB Detent (when clear of obstacles). 56FMC-00 3-14 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration THRUST REVERSER UNLOCK LIGHT ON IN FLIGHT 2. Thrust Reverser Levers - CHECK THRUST REVERSER LEVERS AT STOWED (FULL FORWARD) POSITION. IF LIGHT WILL NOT EXTINGUISH 3. L/R THRUST REVERSER Circuit Breakers (LH panel) - CHECK IN. 4. Airspeed - MAINTAIN 200 KIAS or below. 5. Altitude - FL310 or below. 6. Land as soon as practical (affected thrust reverser will be inoperative). THRUST REVERSER ARM LIGHT ON IN FLIGHT 1. Thrust Reverser Levers - CHECK THRUST REVERSER LEVERS AT STOWED (FULL FORWARD) POSITION. 2. Emergency STOW Switch (affected engine) - Verify NORM. IF ARM LIGHT IS STILL ILLUMINATED 3. HYD PRESS caution light - CHECK. IF HYD PRESS CAUTION LIGHT IS NOT ILLUMINATED 4. Land as soon as practical. IF HYD PRESS CAUTION LIGHT IS ILLUMINATED (THRUST REVERSER ISOLATION VALVE IS OPEN) 4. Emergency STOW Switch (affected engine) - EMER. 5. Airspeed - MAINTAIN 200 KIAS or below. 6. Altitude - FL310 or below. 7. Land as soon as practical (affected thrust reverser will be inoperative). 1. Emergency STOW Switch (affected engine) - EMER. 3-15 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration OVERPRESSURIZATION 1. Pressurization SYSTEM SELECT - MANUAL. Control pressurization with the manual toggle switch. IF STILL OVERPRESSURIZED 2. PRESS SOURCE Select Knob - L or R; control cabin pressure with throttle corresponding to the selected source. IF UNABLE TO CONTROL 3. Oxygen Masks - DON and 100% OXYGEN. 4. Microphone Switches - MIC OXY MASK. NOTE Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. 5. Oxygen Control Valve - MANUAL DROP. 6. Passenger Oxygen - ENSURE passengers are receiving oxygen. 7. Passenger Advisory Lights - PASS SAFETY. 8. PRESS SOURCE Select Knob - OFF. 9. Descend to 15,000 feet MSL or Minimum Safe Altitude, whichever is higher. IF STILL OVERPRESSURIZED 10. EMER DUMP Switch - ON. 11. Refer to Emergency Procedures, EMERGENCY DESCENT and Abnormal Procedures, USE OF SUPPLEMENTAL OXYGEN. 56FMC-00 3-16 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration CABIN DECOMPRESSION (CAB ALT WARNING LIGHT ON) 4. PRESS SOURCE Select Knob - NORM. 5. Passenger Oxygen - ENSURE passengers are receiving oxygen (MANUAL DROP as required). 6. Transponder - EMERGENCY. NOTE • Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. • The passenger oxygen masks will deploy automatically when cabin altitude exceeds 14,500 feet ±500 feet. • If a high altitude airport (field elevation greater than 8,000 feet MSL) is selected on the cabin pressurization controller, the CAB ALT warning light will illuminate at 14,500 feet ±500 feet. IF NOT ARRESTED BY 14,000 FEET CABIN ALTITUDE 7. PRESS SOURCE Select Knob - EMER (control cabin temperature with LH throttle). NOTE The emergency pressurization system will automatically activate when cabin altitude exceeds 14,500 feet ±500 feet and will automatically deactivate when cabin altitude descends below this altitude. 8. PRESS SOURCE Select Knob - NORM (when below 10,000 feet MSL). 9. Refer to Abnormal Procedures, USE OF SUPPLEMENTAL OXYGEN. 10. Land as soon as practical. IF ARRESTED BELOW 14,000 FEET CABIN ALTITUDE 7. Refer to Abnormal Procedures, USE OF SUPPLEMENTAL OXYGEN. 8. Land as soon as practical. 1. Oxygen Masks - DON and 100% Oxygen. 2. Microphone Switches - MIC OXY MASK. 3. Emergency Descent - AS REQUIRED. Refer to Emergency Procedures, EMERGENCY DESCENT. 3-17 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration CABIN PRESSURIZATION CONTROLLER FAILURE (RED LED ILLUMINATED) NOTE Detection of an internal controller fault will be indicated by both SET ALT and RATE displays blanking and the illumination of a red LED in the upper left corner of the controller face. IF CABIN ALTITUDE IS NOT BEING MAINTAINED (CABIN ALTITUDE INCREASING/ DECREASING) 1. Pressurization SYSTEM SELECT Switch - MANUAL. 2. Manual Toggle Switch - UP/DOWN to control cabin altitude. CAUTION CAUTION CABIN MUST BE MANUALLY DE-PRESSURIZED PRIOR TO LANDING. IF CABIN ALTITUDE IS BEING MAINTAINED (CABIN ALTIMETER STEADY) 1. Cabin Altitude - MONITOR. 2. Pressurization SYSTEM SELECT - Be prepared to select MANUAL prior to airplane altitude change. EMERGENCY DESCENT 5. Airspeed - M MO /VMO (use reduced speed if structural damage has occurred). 6. Transponder - EMERGENCY. 7. Passenger Advisory Lights - PASS SAFETY. 8. ATC - ADVISE and obtain local altimeter setting. 9. Altitude - 10,000 feet MSL or Minimum Safe Altitude, whichever is higher. NOTE If terrain or other circumstances prevent a direct descent to 10,000 feet MSL, the descent to 10,000 feet MSL should be completed within 25 minutes of the initiation of the emergency descent. 10. OXYGEN CONTROL VALVE – CREW ONLY (at 10,000 feet MSL and below). IF DESCENT INTO ICING CONDITIONS IS REQUIRED 11. Anti-Ice/Deice - AS REQUIRED. 12. Throttles - AS REQUIRED, maintain sufficient thrust for wing anti-icing (WING ANTI-ICE lights extinguished). 1. AP TRIM DISC Button - PRESS and RELEASE. 2. Throttles - IDLE. 3. Speed Brakes - EXTEND. 4. Airplane Pitch Attitude - INITIALLY TARGET 20 DEGREES NOSE DOWN ATTITUDE. 56FMC-00 3-18 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration ENVIRONMENTAL SYSTEM SMOKE OR ODOR NOTE Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. 3. Smoke Goggles - DON (if required). 4. Cabin OVHD Fan - OFF. 5. DEFOG Fan - OFF. 6. PRESS SOURCE Select Knob - Isolate source by first selecting L. NOTE The PRESS SOURCE Select Knob must remain in each position long enough to allow adequate system purging to determine the source of smoke (approximately 1 minute). IF SMOKE CONTINUES 7. PRESS SOURCE Select Knob - R (allow time for smoke to dissipate). IF SMOKE STILL CONTINUES 8. PRESS SOURCE Select Knob - EMER (control cabin temperature with LH throttle). 9. Refer to Emergency Procedures, SMOKE REMOVAL. 1. Oxygen Masks - DON and EMER. 2. Microphone Switches - MIC OXY MASK. 3-19 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration SMOKE REMOVAL NOTE No action is normally required; however, if smoke is intense: NOTE Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. 3. Smoke Goggles - DON (if required). 4. PASS OXY Knob (if fire source is known and away from oxygen system) - AS APPROPRIATE (assure passengers are receiving oxygen). NOTE Selection of the passenger oxygen system to ON may be appropriate in situations where the flight crew determines it is safe to do so and where supplemental oxygen may assist the passengers’ breathing in a smoke filled cabin. 5. Cockpit Divider - OPEN. 6. Passenger Advisory Light - PASS SAFETY. 7. EMER DUMP Switch - ON for normal power (utilize the manual toggle switch for emergency power situations). NOTE Cabin altitude will not exceed approximately 14,000 feet. 8. Refer to Abnormal Procedures, USE OF SUPPLEMENTAL OXYGEN. IF SMOKE PERSISTS OR IT CANNOT BE VERIFIED THAT THERE IS NO FIRE 9. Land as soon as possible. WARNING WHETHER OR NOT SMOKE HAS DISSIPATED, IF IT CANNOT BE VISIBLY CONFIRMED THAT ANY FIRE HAS BEEN EXTINGUISHED FOLLOWING FIRE SUPPRESSION AND/OR SMOKE EVACUATION PROCEDURE, LAND IMMEDIATELY AT THE NEAREST SUITABLE AIRPORT. 1. Oxygen Masks - DON and EMER. 2. Microphone Switches - MIC OXY MASK. 56FMC-00 3-20 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration ELECTRICAL FIRE OR SMOKE 3. Smoke Goggles - DON (if required). 4. PRESS SOURCE Select Knob - NORM. NOTE Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. KNOWN SOURCE 5. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate. 6. Land as soon as practical. UNKNOWN SOURCE 5. INTERIOR MASTER Switch - OFF. 6. Overhead FLOOD LTS - FULL BRIGHT. 7. BATT Switch - EMER. 8. L/R GEN Switches - OFF - With the battery switch in EMER and the generators OFF, a properly charged battery will supply power for approximately 30 minutes to the following equipment: CAUTION CAUTION WHEN LANDING WITH EMERGENCY POWER (BATTERY SWITCH-EMER AND BOTH GENERATORS OFF), THE FOLLOWING ARE NOT AVAILABLE: • THE ANTISKID/POWER BRAKE SYSTEM IS INOPERATIVE; ONLY THE EMERGENCY BRAKE SYSTEM IS AVAILABLE. • THE WING AND ENGINE ANTI-ICE VALVES WILL BE OPEN. ANTI-ICE ON THRUST CHARTS APPLY. • THE CABIN MUST BE DEPRESSURIZED WITH THE MANUAL TOGGLE SWITCH. THE EMERGENCY DUMP SWITCH IS INOPERATIVE. • ALL EIS INDICATIONS ON THE MFD ARE INOPERATIVE. • NEITHER PFD NOR MFD WILL BE OPERATIONAL. • TRANSPONDER, TCAS AND HF RADIO ARE INOPERATIVE. (Continued Next Page) 1. Oxygen Masks - DON and EMER. 2. Microphone Switches - MIC OXY MASK. COMM 1 Standby Engine Instrument Interior Entry Lights NAV 1 LH Pitot and Static Heaters Standby Flight Display RTU 1 Landing Gear Control & Indication Standby Pitot and Static Heaters ADC 1 Overhead Flood Lights Flap Control ADF 1 Pilot’s and Copilot’s Audio Panels AHRS 2 3-21 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration ELECTRICAL FIRE OR SMOKE (Continued) NOTE • The standby flight display will continue to operate on its own emergency battery pack. This battery pack will allow the standby flight display to operate for 3 hours and 58 minutes. • Sideslips of one ball or greater can cause the Secondary Flight Display airspeed to oscillate and may momentarily indicate up to 9 knots slow when at V REF with landing gear and flaps extended. Maintain coordinated flight until landing flare. 9. WINDSHIELD BLEED AIR Knobs - OFF UNLESS REQUIRED FOR ANTI-ICING. 10. Land as soon as practical (within 30 minutes). IF SEVERITY OF SMOKE WARRANTS 11. Initiate Emergency Procedures, SMOKE REMOVAL and/or EMERGENCY DESCENT. 12. Land as soon as possible. COCKPIT FIRE 13. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (under copilot’s seat). 14. Fire - LOCATE and EXTINGUISH. 15. Land as soon as possible. CABIN FIRE 13. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (aft cabin behind the aft, left seat). 14. Fire - LOCATE and EXTINGUISH. 15. Land as soon as possible. WARNING WHETHER OR NOT SMOKE HAS DISSIPATED, IF IT CANNOT BE VISIBLY CONFIRMED THAT ANY FIRE HAS BEEN EXTINGUISHED FOLLOWING F I R E S U P P R E S S I O N A N D / O R S M O K E E VA C U AT I O N , L A N D IMMEDIATELY AT THE NEAREST SUITABLE AIRPORT. APPROACH 16. Landing Data - COMPUTE and SET. a. Airspeed - VAPP/VREF. b. Landing Distance - Multiply by 1.6 for emergency braking. 17. Crew Briefing - COMPLETE. 18. Avionics and Flight Instruments - CHECK and SET. 19. Passenger Advisory Lights - PASS SAFETY. 20. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure. 21. Flaps - AS REQUIRED. 22. Airspeed - VAPP + 10 KIAS minimum when flaps at 15°. 23. Annunciators - CHECK. WHEN LANDING ASSURED 24. Pressurization - ZERO DIFFERENTIAL PRIOR TO LANDING. 25. Landing Gear - DOWN. 26. Flaps - LAND (35 °) . 27. Airspeed - VREF. 28. Landing - Use emergency brake system. Refer to Abnormal Procedures, WHEEL BRAKE FAILURE. 56FMC-00 3-22 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration BATTERY OVERTEMPERATURE (BATT O’TEMP WARNING LIGHT ON) NOTE If current decreases and battery voltage is 1 volt less than generator voltage in 30 seconds to 2 minutes, monitor battery overheat annunciator for possible change. IF NO VOLT/AMP DECREASE (Battery Relay Stuck) 4. BATT Switch - BATT. 5. BATTERY DISCONNECT Switch (LH panel) - LIFT GUARD AND DISC. 6. Amperage - NOTE DECREASE. IF BATT O’TEMP WARNING LIGHT DOES NOT GO OUT OR >160° WARNING LIGHT FLASHES 7. Land as soon as possible. IF BATT O’TEMP WARNING LIGHT GOES OUT 7. BATTERY DISCONNECT Switch (LH panel) - NORM AND CLOSE GUARD. 8. Land as soon as practical. IF VOLT/AMP DECREASE 4. BATT Switch - OFF (voltmeter will be inoperative). IF BATT O’TEMP WARNING LIGHT GOES OUT 5. BATT Switch - BATT. 6. Continue flight (as desired). CAUTION CAUTION • PROLONGED OPERATION WITH THE BATTERY DISCONNECT SWITCH DISCONNECTED AND THE BATT SWITCH ON WILL GRADUALLY DEPLETE THE BATTERY THROUGH THE BATTERY DISCONNECT RELAY. STARTER ASSISTED AIRSTARTS WILL NOT BE AVAILABLE. • AFTER LANDING, REFER TO AIRPLANE MAINTENANCE MANUAL FOR PROPER MAINTENANCE PROCEDURES, AS DAMAGE TO THE BATTERY MAY HAVE OCCURRED. 1. Amperage - NOTE. 2. BATT Switch - EMER. 3. Amperage - NOTE DECREASE. 3-23 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTER WARNING) 1. L/R GEN Switches - RESET THEN GEN. IF NEITHER GENERATOR COMES ON 2. Overhead FLOOD LTS - FULL BRIGHT. 3. BATT Switch - EMER. With the battery switch in EMER and the generators OFF, a properly charged battery will supply power for approximately 30 minutes to the following equipment: CAUTION CAUTION WHEN LANDING WITH EMERGENCY POWER (BATTERY SWITCH-EMER AND BOTH GENERATORS OFF), THE FOLLOWING ARE NOT AVAILABLE: • THE ANTISKID/POWER BRAKE SYSTEM IS INOPERATIVE; ONLY THE EMERGENCY BRAKE SYSTEM IS AVAILABLE. • THE WING AND ENGINE ANTI-ICE VALVES WILL BE OPEN. ANTI-ICE ON THRUST CHARTS APPLY. • THE CABIN MUST BE DEPRESSURIZED WITH THE MANUAL TOGGLE SWITCH. THE EMERGENCY DUMP SWITCH IS INOPERATIVE. • ALL EIS INDICATIONS ON THE MFD ARE INOPERATIVE. • NEITHER PFD NOR MFD WILL BE OPERATIONAL. • TRANSPONDER, TCAS AND HF RADIO ARE INOPERATIVE. NOTE • The standby flight display will continue to operate on its own emergency battery pack. This battery pack will allow the standby flight display to operate for 3 hours and 58 minutes. • Sideslips of one ball or greater can cause the Secondary Flight Display airspeed to oscillate and may momentarily indicate up to 9 knots slow when at V REF with landing gear and flaps extended. Maintain coordinated flight until landing flare. 4. WINDSHIELD BLEED AIR Knobs - OFF UNLESS REQUIRED FOR ANTI-ICING. 5. Land as soon as practical (within 30 minutes). (Continued Next Page) COMM 1 Standby Engine Instrument Interior Entry Lights NAV 1 LH Pitot and Static Heaters Standby Flight Display RTU 1 Landing Gear Control & Indication Standby Pitot and Static Heaters ADC 1 Overhead Flood Lights Flap Control ADF 1 Pilot’s and Copilot’s Audio Panels AHRS 2 56FMC-00 3-24 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTER WARNING) (Continued) APPROACH 6. Landing Data - COMPUTE and SET. a. Airspeed - VAPP/VREF. b. Landing Distance - Multiply by 1.6 for emergency braking. 7. Crew Briefing - COMPLETE. 8. Avionics and Flight Instruments - CHECK and SET. 9. Passenger Advisory Lights - PASS SAFETY. 10. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure. 11. Flaps - AS REQUIRED. 12. Airspeed - VAPP + 10 KIAS minimum when flaps at 15°. 13. Annunciators - CHECK. WHEN LANDING ASSURED 14. Pressurization - ZERO DIFFERENTIAL PRIOR TO LANDING (use manual toggle switch to depressurize cabin). 15. Landing Gear - DOWN. 16. Flaps - LAND (35 °) . 17. Airspeed - VREF. 18. Landing - Use emergency brake system. Refer to Abnormal Procedures, WHEEL BRAKE FAILURE. IF ONLY ONE GENERATOR COMES ON 2. Electrical Load - REDUCE as required. 3. Air Conditioner Compressor - OFF or FAN. NOTE The Interior Master Switch, located on the LH Oxygen Panel, will shed all non- essential passenger cabin electrical loads. AUTOPILOT MALFUNCTION AUTOPILOT OUT OF TRIM (RED BOXED “EK,L” OR “AI,J” ON PFD’s) Illumination of a red boxed “E” or “A” annunciation on the PFD indicates the autopilot is flying in a mistrimmed condition. CAUTION CAUTION DO NOT MANUALLY OVERPOWER THE AUTOPILOT. OVERPOWERING THE AUTOPILOT DOES NOT CANCEL THE AUTOTRIM. THE AUTOTRIM WILL TRIM AGAINST FLIGHT CREW INPUTS TO THE COLUMN/WHEEL. THIS COULD LEAD TO A SEVERE OUT-OF-TRIM CONDITION. IF MANUAL CONTROL OF THE AIRPLANE IS REQUIRED, DISENGAGE THE AUTOPILOT WITH THE AUTOPILOT/TRIM DISENGAGE BUTTON. 1. Control Wheel - GRIP WITH BOTH HANDS. CAUTION CAUTION BE PREPARED FOR CONTROL WHEEL FORCES IN EXCESS OF 25 POUNDS. 2. AP/TRIM DISC Button - PRESS AND RELEASE. 3. Elevator or Aileron Trim - ADJUST as required. 4. Autopilot - ENGAGE as desired. 1. AP TRIM DISC Switch - PRESS and RELEASE. AA 3-25 56FMC-00 MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration PFD ATTITUDE FAILURE - SINGLE (RED AP, RED ATT AND WHITE XAHS DISPLAYED ON ONE PFD) 1. AHRS Reversion (Affected Side) - AHRS REV. 2. AP XFR - PUSH, select side with operating AHRS, if required. 3. Flight Director Mode Selectors - Select modes as desired. NOTE Autopilot will not engage. Flight director will not be displayed unless side with operating AHRS is selected. 4. Land as soon as practical. PFD ATTITUDE FAILURE - DUAL (RED AP, RED ATT, AND WHITE XAHS ON BOTH PFD’S) 1. Airplane Attitude - CONTROL by reference to standby flight display. 2. Land as soon as practical. PFD HEADING FAILURE - SINGLE (RED AP, RED HDG AND WHITE XAHS DISPLAYED ON ONE PFD) 1. AHRS Reversion (Affected Side) - AHRS REV. 2. AP XFR - PUSH, select side with operating AHRS, if required. 3. Flight Director Mode Selectors - Select modes as desired. NOTE Autopilot will not engage. Flight director will not be displayed unless side with operating AHRS is selected. 4. Land as soon as practical. PFD HEADING FAILURE - DUAL (RED AP, RED HDG, AND WHITE XAHS ON BOTH PFD’S) 1. Airplane Heading - CONTROL by reference to standby flight display. 2. Land as soon as practical. 56FMC-00 3-26 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration AIR DATA COMPUTER FAILURE - SINGLE (RED IAS/ALT/VS DISPLAYED ON ONE PFD) 1. DADC REV Switch (Affected Side) - REV. 2. AP XFR - PUSH, select side with operating ADC, if required. 3. Autopilot Mode Selector - Select modes as desired. NOTE The flight director will not display and the autopilot will engage only in basic pitch and roll mode unless the side with operating ADC is selected with AP XFR. 4. RTU - Select XPNDR on side with operating ADC. 5. Land as soon as practical, if ADC 1 has failed refer to Abnormal Procedures, CABIN PRESSURIZATION CONTROLLER FAILURE. CAUTION CAUTION DEPENDING ON THE CAUSE OF THE FAILURE, THE PRESSURIZATION CONTROLLER MAY BE IN ISOBARIC MODE. STRUCTURAL DAMAGE IS POSSIBLE IF THE LANDING IS ACCOMPLISHED WITH THE CABIN PRESSURIZED. AIR DATA COMPUTER FAILURE - DUAL (RED IAS/ALT/VS ON BOTH PFD’S) 1. Airplane Airspeed and Altitude - FLY AIRCRAFT by reference to standby flight display. 2. Land as soon as practical, refer to Abnormal Procedures, CABIN PRESSURIZATION CONTROLLER FAILURE. CAUTION CAUTION DEPENDING ON THE CAUSE OF THE FAILURE, THE PRESSURIZATION CONTROLLER MAY BE IN ISOBARIC MODE. STRUCTURAL DAMAGE IS POSSIBLE IF THE LANDING IS ACCOMPLISHED WITH THE CABIN PRESSURIZED. NOTE The flight director will not display and the autopilot will engage only in basic pitch and roll mode. Transponder altitude reporting will be inoperative. RED BOXED FD DISPLAYED ON PFD (FLIGHT GUIDANCE COMPUTER FAILURE) NOTE • Failure of AHRS or DADC on the coupled side during normal operation will result in Flight Guidance Computer failure. • Vertical/Lateral modes with an amber strike-through line indicate the autopilot is in basic pitch and roll. • Indication of loss of NAV data from an ILS approach. • Normal after landing from an ILS, when passing the GS antenna. 1. AP XFR Button - PUSH (if required); select side with operating AHRS and ADC. 2. Flight Director Modes - RESELECT as desired. 3. Autopilot - ENGAGE as desired (if an AHRS failure occurred, autopilot will not engage). 3-27 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration RED AOA1 OR AOA2 DISPLAYED ON PFD (LOW SPEED CUE (LSC) AOA FAILURE) Indicates AOA information is not valid. NOTE The default LSC indication is a default amber vertical line displayed on top of the ISS (Impending Stall Speed) checkerboard. The amber vertical line represents the minimum and maximum stall speeds, 69 KIAS to 97 KIAS. RED DCP 1 OR DCP 2 DISPLAYED ON PFD (DISPLAY CONTROL PANEL FAILURE) IF DCP 1 DISPLAYED 1. AP XFR Button - PUSH (if required). Select Copilot side. 2. Copilot DCP - Utilize to control DCP functions displayed on Copilot PFD and reference speeds on both PFDs. The course heading panel (CHP) will be inoperative. IF DCP 2 DISPLAYED 1. AP XFR Button - PUSH (if required). Select Pilot side. 2. Pilot DCP and CHP - Utilize to control DCP functions displayed on Pilot PFD and reference speeds on both PFDs. NOTE The copilot course knob panel (CKP) will be inoperative. 1. Airspeed - Flaps 0o = VAPP + 10 KIAS Flaps 7o = VAPP + 5 KIAS Flaps 15o = VAPP Flaps 35o = V REF 56FMC-00 3-28 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration ELECTRIC ELEVATOR RUNAWAY TRIM 2. Throttles - As required to control airspeed. 3. Manual Elevator Trim - AS REQUIRED. 4. PITCH TRIM Circuit Breaker (LH panel) - PULL. 5. AP TRIM DISC Switch - RELEASE. NOTE Do not attempt to use the autopilot if the electric trim is inoperative. The autopilot will not be able to trim out servo torque, and disengaging the autopilot could result in a significant pitch upset. EMERGENCY EVACUATION 6. Airplane and Immediate Area - CHECK for BEST ESCAPE ROUTE. IF THRU CABIN DOOR 7. Cabin Door - OPEN. 8. Move away from airplane. IF THRU EMERGENCY EXIT 7. Emergency Exit - REMOVE and THROW OUT of airplane. 8. Move away from airplane. 1. AP TRIM DISC Switch - PRESS and HOLD. 1. Parking Brake - SET. 2. Throttles - BOTH OFF. 3. LH/RH ENGINE FIRE Switches - BOTH PRESS. 4. LH/RH Fire Bottle Armed Switches - BOTH PRESS (if fire suspected). 5. BATT Switch - OFF. 3-29 56FMC-00 AA MODEL 560 SECTION III - OPERATING PROCEDURES EMERGENCY PROCEDURES FAA APPROVED U.S. Configuration DITCHING Ditching is not approved under 14 CFR 25.801 and was not conducted during certification testing of the airplane. Should ditching be required, the following procedures are recommended: PRELIMINARY 1. PRESS SOURCE Select Knob - OFF (A/C Altitude < 10,000 Feet MSL). 2. Radio - MAYDAY. 3. Transponder - Emergency (7700). 4. Emergency Locator Beacon - ON. 5. ATC - ADVISE. 6. Passenger Advisory Lights - PASS SAFETY. 7. Passengers - BRIEF. a. Verify passenger seats are full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure, and stow loose items securely. b. Don life vests (do not inflate). 8. Ditching Heading - Parallel to Major Swell System. APPROACH 1. Landing Gear - UP. 2. Speed Brakes - RETRACT. 3. Flaps - LAND (35°) (aural gear warning will not cancel). 4. Rate of Descent - 200 to 300 feet/minute (maintain VREF ). 5. Approach Speed - V REF. NOTE Plan approach to parallel any uniform swell pattern and attempt to touch down along a wave crest or just behind it. If the surface wind is very strong or the water surface rough and irregular, ditch into the wind on the back side of a wave. WATER CONTACT 1. Aircraft Pitch Attitude - Slightly higher than Normal Landing Attitude. 2. Reduce airspeed and rate of descent to a minimum, but do not stall the airplane. 3. Throttles - OFF just prior to water contact and contact water on a crest of a swell, parallel to the major swell. AFTER WATER CONTACT Depending on sea conditions, multiple impacts can be expected. Seat belts should not be released until the airplane has come to a complete stop. Under reasonable ditching conditions, the aircraft should remain afloat an adequate time to launch and board life rafts in an orderly manner. WARNING THE MAIN CABIN DOOR SHOULD REMAIN CLOSED AND EVACUATION MADE THROUGH THE EMERGENCY EXIT. 56FMC-00 3-30 AA MODEL 560 SECTION III - OPERATING PROCEDURES ABNORMAL PROCEDURES FAA APPROVED U.S. Configuration ABNORMAL PROCEDURES TABLE OF CONTENTS PAGE ABNORMAL PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-35 ENGINE/FUEL Engine Failure/Precautionary Shutdown. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-35 In-flight Restart - One Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-35 Engine Start Malfunction (Engine Does Not Start on Ground) . . . . . . . . . . . . . . . . . . . . . . . . 3-36 Engine Starter Will Not Disengage (L or R ENGINE START Button Light On After Engine Start) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-36 High Sustained ITT During Ground Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-36 Airstart Envelope. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-37 Oil Filter Bypass (OIL FLTR BP L or R Caution Light On) . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-38 Low Fuel Pressure (LO FUEL PRESS L or R Caution Light On) . . . . . . . . . . . . . . . . . . . . . . 3-38 Low Fuel Quantity (LO FUEL LEVEL L or R Caution Light On) . . . . . . . . . . . . . . . . . . . . . . . 3-38 Fuel Boost Pump On (FUEL BOOST L or R Caution Light On) . . . . . . . . . . . . . . . . . . . . . . . 3-38 Fuel Filter Bypass (FUEL FLTR BP L or R Caution Light On) . . . . . . . . . . . . . . . . . . . . . . . . 3-38 N1 , N2 or ITT Failure (Amber Dashes in Digital Readout and/or Fail Message) . . . . . . . . . . . 3-39 N1 Bug Amber . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39 Engine Control System fault (ENG CNTL SYS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39 Loss of Oil Temperature Indication (No Pointers Displayed). . . . . . . . . . . . . . . . . . . . . . . . . . 3-40 Loss of Fuel Quantity Indication (No Pointer and Amber Dashes in Digital Readout) . . . . . . 3-40 Loss of Fuel Flow Indication (Amber Dashes Displayed in Digital Readout) . . . . . . . . . . . . . 3-40 Firewall Shutoff Valve Closed (F/W SHUTOFF L or R Caution Light On). . . . . . . . . . . . . . . . 3-41 Engine Fire Detection System Failure (FIRE DET SYS L or R Caution Light On) . . . . . . . . . 3-41 Ground Idle (GND IDLE Advisory Light On) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-41 Engine Vibration (ENG VIB L or R Advisory Light On) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-42 Fuel Gauging System Fault (FUEL GAUGE L or R Caution Light On) . . . . . . . . . . . . . . . . . . 3-42 ELECTRICAL Single Generator Failure (GEN OFF L or R Caution Light On). . . . . . . . . . . . . . . . . . . . . . . . 3-42 Aft J-Box Current Limiter or Circuit Breaker (AFT J BOX LMT or CB Caution Light On) . . . . 3-43 ENVIRONMENTAL/PRESSURIZATION Engine Bleed Air Overheat (BLD AIR O'HEAT L or R Caution Light On) . . . . . . . . . . . . . . . . 3-43 Environmental System Air Duct Overheat (AIR DUCT O'HEAT Caution Light On) . . . . . . . . 3-44 Automatic Temperature Controller Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-44 Emergency Pressurization On (Automatic Actuation) (EMER PRESS Caution Light On) and Cabin Altitude (CAB ALT Warning Not On) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-45 Cabin Pressurization Controller Failure (Amber LED Illuminated) . . . . . . . . . . . . . . . . . . . . . 3-45 Air Cycle Machine Overheat (ACM O'HEAT Caution Light On) . . . . . . . . . . . . . . . . . . . . . . . 3-46 (Continued Next Page) 3-31 56FMC-00 MODEL 560 SECTION III - OPERATING PROCEDURES ABNORMAL PROCEDURES FAA APPROVED U.S. Configuration TABLE OF CONTENTS (Continued) PAGE FLIGHT CONTROLS Electric Trim Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-46 Jammed Elevator Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-47 Landing With Failed Primary Flight Control Cable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-48 ICING Wing Anti-Ice Failure (WING ANTI-ICE L or R Caution Light On and Master Caution) . . . . . 3-49 Engine Anti-ice Failure (ENG ANTI-ICE L or R Caution Light On and Master Caution) . . . . . 3-51 Wing Bleed Air Overheat (WING O'HEAT L or R Caution Light On). . . . . . . . . . . . . . . . . . . . 3-51 Tail Deice Failure (TL DEICE FAIL L or R Caution Light On) . . . . . . . . . . . . . . . . . . . . . . . . . 3-52 Tail Deice Timer Failure (TL DEICE PRESS L or R Advisory Light Fails To Illuminate or Continues To Cycle or TL Deice Press Remains Illuminated with Switch in Auto or Off) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-53 Windshield Air Overheat (WS AIR O'HEAT Caution Light On) . . . . . . . . . . . . . . . . . . . . . . . . 3-54 Windshield Bleed Air Failure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-55 Pitot-Static Heater Failure (P/S HTR L or R, or STBY P/S HTR Caution Light On) . . . . . . . . 3-55 Angle-of-Attack Probe Heater Failure (AOA HTR FAIL Caution Light On) . . . . . . . . . . . . . . . 3-56 TT0 Heater Failure (TTO HTR FAIL) . . . . . . .